JPS6038296A - Cooling system of guided missile - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a cooling system for a guided flying vehicle carrying electronic equipment that requires cooling.

In recent years, guided flying vehicles have become more densely packed with onboard electronic equipment, and seeker activation has become more active.

The amount of heat generated by electronic devices is increasing.

Instead, the guided flying object maintains its function. Alternatively, sufficient cooling of electronic equipment has become necessary to improve the situation.

FIG. 1 shows a conventional cooling system for a guided flying vehicle. In the figure, (1) is an electronic device, (2) is a circulation pump, (3) is a tank, and (4) is a refrigerator. The coolant for cooling the electronic device (1) is stored in the tank (3), and is sent to the electronic device (1+) by the pump (2). The liquid is cooled by a refrigerator and returned to the tank (3).

Here, the refrigerator (4) has a complex mechanism composed of many elements, so it is easy to make it smaller and lighter.
:1, which was a major limiting factor in making the cooling system smaller and lighter. Furthermore, there is a problem in that the internal temperature of the guided flying object increases due to the heat discharged from the refrigerator (4), resulting in a decrease in refrigeration efficiency.

This invention was made to eliminate the above-mentioned drawbacks, and will be explained in detail below.

Figure 2 shows the cooling system for a guided flying vehicle according to the present invention, which consists of two high-pressure air sources (6) on the launcher (5) side, a dehumidifier (7), and a vortex tube (8). It is stored near the low temperature air supply system and the electronic equipment room θ of the guided flying object (9). Electronic equipment that requires cooling (1), circulation pump (2), tank (3), air-to-liquid heat exchanger 0υ
A circulating liquid cooling system consisting of multiple piping lines, a temperature sensor H that detects the temperature of the cooling liquid, and a pulp θ that controls the flow rate of cooling air.
It consists of a temperature control system consisting of a temperature control system.

The vortex tube (8) discharges high-temperature air and low-temperature air by injecting high-pressure air. 2For example, if the air flows in at a pressure of about rkg/crd, the air is about 40°C lower than the inflow side temperature. Therefore, the volume of the heat exchanger can be reduced, and the cooling system in the guided flying object can be made compact.

Next, the operating principle will be explained.

When the system starts operating with the guided flying vehicle (9) attached to the launcher (5), the pump (2) operates, circulates the coolant, and begins cooling the electronic equipment (1). do. At the same time, the high pressure air source ('6) is activated and starts supplying compressed air. The compressed air enters the vortex tube (8) after being dehumidified in the dehumidifier (7). Here, high-temperature air is discharged to the outside of the launcher through the exhaust hole (14), and low-temperature air is sent through the self-sealing quick coupler 〇e to the heat exchanger aυ, where the coolant and stain equipment ( 1)
It absorbs heat from the air and sends it to the electronic equipment room OI. A pressure regulating valve αe is attached to the electronic equipment room 01, and when the internal pressure becomes higher than a preset pressure, the valve automatically opens and the air in the electronic equipment room α is discharged to the outside of the machine.

Furthermore, the temperature of the coolant is constantly detected by a temperature sensor Q, and is input to the controller QIIO via an umbilical connector aη. Using this temperature signal, the temperature of the coolant can be controlled to the set value by changing the amount of heat exchange in the controller (+1 opens and closes the compressed air flow rate control pulp 0 and heat exchanger 01). .

After the guided flying vehicle (9) is launched, the supply of cooling air from the first launcher (5) is cut off, but by continuing to circulate the pre-cooled coolant), the sensible heat of the coolant is utilized. Thus, the electronic device (1) can be maintained at a temperature below the permissible temperature during flight.

As described above, according to the present invention, it is lightweight and small,
A cooling system that can easily control the temperature can be constructed, and as a result, a guided flying object can be provided that can mount high-power electronic equipment.

[Brief explanation of the drawing]

FIG. 1 is a schematic diagram of a conventional cooling system for a guided flying vehicle, and FIG. 2 is a diagram of a cooling system for a guided flying vehicle according to the present invention. In the figure, (1) is an electronic device that requires cooling, (2) is a circulation pump, (3) is a tank, (4) is a refrigerator, (5) is a launcher, (6) is a high pressure air source, and (7 ) is a dehumidifier, (8) is a vortex tube, (9) is a guided flying object, and H is an electronic equipment room. I is the heat exchanger, Q3 is the temperature sensor, (Im is the flow control pulse 7', Q4 is the exhaust hole, (I!9 is the self-sealing quick coupler, αe is the pressure regulating valve, a is the umbilical connector, (18 is a controller. In addition, the same or corresponding parts in the figure are indicated by the same reference numerals.
− is. Agent Masuo Oiwa

Claims (1)

[Claims] In a cooling system for a guided flying vehicle, there are electronic devices that require liquid cooling, a tank that stores the coolant that has flowed out from the electronic device, and a tank that has a temperature sensor to detect the temperature of the coolant. A liquid consisting of a heat exchanger for dissipating the heat taken by the electronic device to cooling air, and a pump for sucking the liquid from the tank and circulating it to the electronic device via the heat exchanger. A cold circuit, an air circuit for introducing low-temperature cooling air into the heat exchanger, and a pressure regulating pulp for discharging the air flowing out from the heat exchanger to the outside of the guided flying vehicle are installed in the flying vehicle. In addition to preparing for An air circuit consisting of a dehumidifier and a vortex tube that has the function of separating the compressed air after dehumidification into high temperature air and low temperature cooling air, and receiving the signal from the temperature sensor, A temperature controller for driving the flow rate control pulp is provided in the launcher suspending the flying object, and low-temperature cooling air sent from the vortex tube of the launching device is connected to the air inside the flying object through a quick coupler. A cooling system for a guided flying object, characterized in that it is capable of supplying power to a circuit.